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| United States Patent |
6,155,777
|
|
Aschenbruck
, et al.
|
December 5, 2000
|
Removal of cooling air on the housing side of a diffuser of a compressor
stage of gas turbines
Abstract
The removal of cooling air from the diffuser part of a radial end stage of
a compressor of a gas turbine is provided. Compressed air is removed via a
cooling air discharge (10) from a radial compressor stage, which comprises
a rotor disk (2) and a bladed diffuser (20). The removal of cooling air
may be brought about such that the cooling air is removed on one side
through openings (6) on the housing side (20.1) of the diffuser (20) and
is fed through cooling air channels (10) to the parts in contact with hot
gas, including the outer wall of the bifurcated tube (17). The compressed
air is guided to the diffuser outside (20.2) through cooling air holes
(19) in the diffuser blade (3).
| Inventors:
|
Aschenbruck; Emil (Duisburg, DE);
Ebbing; Hildegard (Oberhausen, DE);
Jeske; Hans Otto (Reppenstedt, DE);
Orth; Ulrich (Bottrop, DE);
Schonenborn; Harald (Wuppertal, DE)
|
| Assignee:
|
GHH Borsig Tubomaschinen GmbH (Oberhausen, DE)
|
| Appl. No.:
|
256575 |
| Filed:
|
February 24, 1999 |
Foreign Application Priority Data
| Apr 01, 1998[DE] | 198 14 627 |
| Current U.S. Class: |
415/115; 415/208.3; 415/226; 415/914 |
| Intern'l Class: |
F01D 009/06 |
| Field of Search: |
415/115,208.2,208.3,208.4,211.1,226,914
60/751
|
References Cited
U.S. Patent Documents
| 2778204 | Jan., 1957 | Frank.
| |
| 4131389 | Dec., 1978 | Perrone et al. | 415/211.
|
| 4368005 | Jan., 1983 | Exley et al. | 415/207.
|
| 4761947 | Aug., 1988 | Hennecke et al. | 415/115.
|
| 5207559 | May., 1993 | Clevenger et al. | 415/166.
|
| Foreign Patent Documents |
| 11 99 541 | Aug., 1965 | DE.
| |
| 43 26 799 A1 | Feb., 1995 | DE.
| |
| 11 19 479 | Jul., 1968 | GB.
| |
Other References
Jack D. Mattingly, 1996, Elements of Gas Turbine Propulsion, McGraw Hill
International Editions Mechanical Engineering Series.
|
Primary Examiner: Look; Edward K.
Assistant Examiner: McDowell; Liam
Attorney, Agent or Firm: McGlew and Tuttle, P.C.
Claims
What is claimed is:
1. A gas turbine compressor radial end stage diffuser part with cooling air
removal, comprising:
a housing wall defining an annular air circulation space, the housing wall
having a cooling air discharge;
a diffuser housing having sides;
diffuser vanes in said diffuser housing; and
openings arranged in a side of said diffuser housing in an area of said
cooling air discharge.
2. The diffuser part in accordance with claim 1, wherein said openings are
round holes.
3. The diffuser part in accordance with claim 1, wherein said openings are
slots extending in a radial direction of the gas turbine compressor radial
end stage.
4. The diffuser part in accordance with claim 1, wherein said openings are
slots extending in a circumferential direction of the gas turbine
compressor radial end stage.
5. A gas turbine compressor radial end stage, comprising:
a compressor housing with a discharge opening;
a housing wall defining an annular air circulation space within said
compressor housing, said annular air circulation space being in fluid
communication with said discharge opening, said housing wall having a
cooling air discharge;
a diffuser housing having sides;
diffuser vanes in said diffuser housing; and
openings arranged in a side of said diffuser housing.
6. The gas turbine compressor radial end stage in accordance with claim 5,
wherein said openings are round holes.
7. The gas turbine compressor radial end stage in accordance with claim 5,
wherein said openings are slots extending in a radial direction of the gas
turbine compressor radial end stage.
8. The gas turbine compressor radial end stage in accordance with claim 5,
wherein said openings are slots extending in a circumferential direction
of the gas turbine compressor radial end stage.
9. The gas turbine compressor radial end stage in accordance with claim 5,
further comprising a passage connecting said openings and said housing
wall cooling air discharge.
10. The gas turbine compressor radial end stage in accordance with claim 9,
wherein said passage comprises a plurality of cooling air holes formed in
a diffuser blade.
11. A gas turbine compressor radial end stage, comprising:
a compressor housing with a discharge opening;
a housing wall defining an annular air circulation space within said
compressor housing, said annular air circulation space being in fluid
communication with said discharge opening, said housing wall having a
plurality of cooling air discharge channels;
compressor rotor blades radially inwardly of said annular space;
a radial compressor end stage with a radial rotor disk and a diffuser with
a diffuser housing having sides and diffuser vanes; and
openings arranged in a side of said diffuser housing, each of said openings
being in fluid communication with one of said air discharge channels.
12. The gas turbine compressor radial end stage in accordance with claim
11, wherein said openings are round holes.
13. The gas turbine compressor radial end stage in accordance with claim
11, wherein said openings are slots extending in a radial direction of the
gas turbine compressor radial end stage.
14. The gas turbine compressor radial end stage in accordance with claim
11, wherein said openings are slots extending in a circumferential
direction of the gas turbine compressor radial end stage.
15. The gas turbine compressor radial end stage in accordance with claim
11, further comprising a passage connecting said openings and said housing
wall cooling air discharge channels to provide said fluid communication
between said openings and said channels.
16. The gas turbine compressor radial end stage in accordance with claim
15, wherein said passage comprises a plurality of cooling air holes formed
in said diffuser blades.
Description
FIELD OF THE INVENTION
The present invention pertains to the removal of cooling air from the
diffuser part of a radial end stage of a compressor of a gas turbine.
BACKGROUND OF THE INVENTION
Cooling air, which is removed from the compressor under high pressure, is
needed to cool the components that are in contact with hot gas in a gas
turbine, which comprises a compressor, a combustion means and a turbine.
In a gas turbine developed by the applicant, compressed air is removed from
a radial stage of a compressor, which is an end stage in this case,
through the housing wall in the diffuser part, which wall is arranged on
the side of the annular space.
This cooling air is removed from the radial compressor stage, which
comprises a rotor disk and a diffuser, which may be either bladed or
unbladed. In the case of a bladed diffuser, the cooling air removed is
transported within the diffuser vanes through horizontal holes in the
direction of the outside of the diffuser. A deadwater space, which reduces
the efficiency of the entire compressor stage, frequently develops in such
a diffuser near the housing wall.
SUMMARY AND OBJECTS OF THE INVENTION
The primary object of the present invention is to design the removal of
cooling air in the compressor part of a gas turbine such that favorable
effects on the compressor efficiency are achieved from a fluidic
viewpoint.
According to the invention cooling air from the diffuser part of a radial
end stage of a compressor of a gas turbine is removed. This is achieved by
providing at least one opening arranged circularly between the diffuser
vanes in the diffuser housing side in the area of a cooling air discharge
provided in a housing wall of an annular space adjacent to the discharge.
The openings may be provided as round holes. The openings may also be slots
extending in the radial direction. The openings may also be slots
extending in the circumferential direction.
Due to the device according to the present invention, the removal of
cooling air is brought about such that the compressed cooling air is
removed through openings in the form of holes or slots on the housing side
of the diffuser and the side wall boundary layer is thus drawn off.
The openings may be designed either as round holes or as slots extending in
the radial direction or extending in the circumferential direction. The
formation of a deadwater area is prevented or at least greatly reduced as
a result, which increases the efficiency of the entire stage.
As a whole, it is achieved by the device according to the present invention
that a deadwater area is avoided, which leads to a reduction in the losses
in the diffusor and to an increase in the efficiency of the stage.
The various features of novelty which characterize the invention are
pointed out with particularity in the claims annexed to and forming a part
of this disclosure. For a better understanding of the invention, its
operating advantages and specific objects attained by its uses, reference
is made to the accompanying drawings and descriptive matter in which
preferred embodiments of the invention are illustrated.
BRIEF DESCRIPTION OF THE DRAWINGS
In the drawings:
FIG. 1 is a longitudinal sectional view through the compressor part of a
gas turbine in the area of the diffuser;
FIG. 2 is an enlarged view of the diffuser according to FIG. 1; and
FIG. 3 is a partially sectional view of the diffuser blades and the housing
wall in the diffuser area with different exemplary embodiments of the
removal of cooling air.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring to the drawings in particular, FIG. 1 shows a longitudinal
section through a compressor of a gas turbine with parts of the annular
space 8, the guide vane interior space 9, the compressor housing 15 and
the discharge opening 16 for the compressed air, which is fed to the
combustion chamber of the gas turbine.
The rotor blades 12 of the compressor are fastened to the rotor disks 13,
which are held together by a plurality of tie rods 14. Guide vanes 11 are
fastened in the vane support 1. The end stage of the compressor comprises
a radial stage with a radial rotor disk 2, a diffuser with blades (vanes)3
and an axial guide vane 18. The compressed air then enters the annular
space 8.
In such a gas turbine, which comprises a compressor, a combustion means and
a turbine, cooling air is needed to cool the components coming into
contact with hot gas, and this cooling air is removed from the compressor
under high pressure.
FIG. 2 shows an enlarged view of the diffuser from FIG. 1. With the
corresponding fastening elements 7, the diffuser blading (diffuser vanes)
3 is also used at the same time to connect the vane support 1 to the
housing wall of the annular space 4.
A deadwater area 5, which reduces the efficiency of the entire compressor
stage, frequently develops in such a diffuser 20 near the housing wall 4
on the diffuser housing side 20.1.
Compressed air is removed via a cooling air discharge 10 from a radial
compressor stage, which comprises a rotor disk 2 and a diffuser 20, which
may be either bladed or unbladed.
The removal of cooling air is therefore brought about according to the
present invention such that the cooling air is removed on one side through
openings 6 on the housing side 20.1 of the diffuser 20 and is fed through
cooling air channels 10 to the parts in contact with hot gas, including
also the outer wall of the bifurcated tube 17.
In the case of a bladed diffuser, the air is guided through cooling air
holes 19 in the diffuser blade 3 to the diffuser outside 20.2. In the case
of an unbladed diffuser 20, the cooling air must be transported to the
diffuser outside by other suitable means.
FIG. 3 shows a view of the housing wall in the diffuser area with various
exemplary embodiments of the removal of cooling air on one side through
openings 6 on the housing side 20.1 of the diffuser 20. The openings 6 are
provided in any one of the three hole types 6.1, 6.2, and 6.3 or in
combinations thereof. The removal may take place either through holes
6.1., through slots extending radially 6.2, or through slots extending in
the circumferential direction 6.3.
While specific embodiments of the invention have been shown and described
in detail to illustrate the application of the principles of the
invention, it will be understood that the invention may be embodied
otherwise without departing from such principles.
______________________________________
List of Reference Numbers
______________________________________
1 Vane support
2 Rotor disk, radial
3 Diffuser vane
4 Housing wall
5 Deadwater in 20
6 Openings in 20.1
6.1 Holes
6.2 Slots, extending in the radial direction
6.3 Slots, extending in the circumferential direction
7 Fastening elements
8 Annular space
9 Vane support interior space
10 Cooling air discharge
11 Guide vane
12 Guide vane
13 Rotor disk
14 Tie rod
15 Compressor housing
16 Discharge opening
17 Bifurcated tube
18 Axial deflecting blades
19 Holes in 3
20 Diffuser
20.1 Diffuser, housing side
20.2 Diffuser, outside
______________________________________
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